Hydraulic control systems and methods for components of an aircraft

ABSTRACT

A hydraulic system for a vehicle includes a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of the vehicle and control flow of hydraulic fluid to actuators of components based on the operational signal. The hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

FIELD OF THE DISCLOSURE

Embodiments of the present disclosure generally relate to hydraulic control systems and methods for components of an aircraft.

BACKGROUND OF THE DISCLOSURE

A commercial aircraft includes various components that are hydraulically controlled. For example, ailerons, spoilers, and flaperons on wings, elevators on a horizontal stabilizer, a rudder on a vertical stabilizer, components of landing gear, and the like can be hydraulically controlled. The components are operatively coupled to one or more actuators that are operated through hydraulic pressure. The actuators are fluidly coupled to a fluid circuit that circulates hydraulic fluid to and from the actuators.

Hydraulic demands for aircraft are variable. While normal aircraft operations do not approach limits of a hydraulic system, certain situations can increase hydraulic demand. For example, during maintenance while the aircraft is on the ground, certain hydraulic pumps can be deactivated. However, certain components can be operated during the maintenance process, but due to the inactivity of certain pumps, there can not be sufficient flow rate of the hydraulic fluid to the components.

As such, the total volume of hydraulic fluid, number of retaining vessels and pumps, and the like can be increased to accommodate additional hydraulic demand. As can be appreciated, however, increasing the amount of hydraulic fluid, retaining vessels, and pumps adds size and weight to an aircraft. The added weight decreases fuel efficiency of the aircraft during operation.

SUMMARY OF THE DISCLOSURE

A need exists for an efficient system and method of managing hydraulic demand of an aircraft. Further, a need exists for a system and method of managing hydraulic demand of an aircraft without adding weight to the aircraft.

With those needs in mind, certain embodiments of the present disclosure provide a hydraulic system. The hydraulic system includes a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of a vehicle, such as an aircraft, and control flow of hydraulic fluid to actuators of components based on the operational signal. The hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system. The hydraulic monitoring control unit is configured to refrain from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.

In at least one embodiment, one or more pumps are fluidly coupled to the actuators through a fluid circuit. The pump(s) are configured to circulate the hydraulic fluid with respect to the actuators.

As an example, the components include ailerons, spoilers, flaperons of wings of the aircraft, elevators of a horizontal stabilizer of the aircraft, and a rudder of a vertical stabilizer of the aircraft.

In at least one embodiment, one or more valves are in fluid communication with the actuators. The hydraulic monitoring control unit is configured to control the valve(s) to control the flow of hydraulic fluid to the actuators of the components.

As an example, the sub-system of the aircraft can include at least one engine. As another example, the sub-system of the aircraft can include at least one pump.

In at least one embodiment, at least one of the actuators includes a fluid inlet connected to a fluid inlet path, a first valve disposed within the fluid inlet path, a second valve disposed within the fluid inlet path downstream from the first valve, a piston connected to the fluid inlet path, a fluid outlet path connected to the piston and having a fluid outlet, and a bypass valve. The first valve and the second valve are also disposed within the fluid outlet path. The hydraulic monitoring control unit is configured to control the first valve, the second valve, and the bypass valve to form a bypass fluid flow path that prevents the hydraulic fluid from passing to the piston in response to the operational signal indicating the altered operational state of the sub-system.

Certain embodiments of the present disclosure provide a hydraulic control method for an aircraft. The hydraulic control method includes receiving (such as by a hydraulic monitoring control unit) an operational signal from a sub-system of the aircraft, and controlling (such as by the hydraulic monitoring control unit) flow of hydraulic fluid to actuators of components based on the operational signal. Said controlling includes bypassing the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

Certain embodiments of the present disclosure provide an aircraft including a sub-system, components, actuators operatively coupled to the components, and a hydraulic system, as described herein.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates a schematic block diagram of a hydraulic system of an aircraft, according to an embodiment of the present disclosure.

FIG. 2 illustrates a front perspective view of an aircraft, according to an exemplary embodiment of the present disclosure.

FIG. 3 illustrates a schematic diagram of components of the aircraft, according to an embodiment of the present disclosure.

FIG. 4 illustrates a schematic diagram of an actuator operating in a normal state, according to an embodiment of the present disclosure.

FIG. 5 illustrates a schematic diagram of the actuator having a bypass valve in a bypass position, according to an embodiment of the present disclosure.

FIG. 6 illustrates a flow chart of a hydraulic control method for an aircraft, according to an embodiment of the present disclosure.

DETAILED DESCRIPTION OF THE DISCLOSURE

The foregoing summary, as well as the following detailed description of certain embodiments will be better understood when read in conjunction with the appended drawings. As used herein, an element or step recited in the singular and preceded by the word “a” or “an” should be understood as not necessarily excluding the plural of the elements or steps. Further, references to “one embodiment” are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features. Moreover, unless explicitly stated to the contrary, embodiments “comprising,” “including,” or “having” an element or a plurality of elements having a particular condition can include additional elements not having that condition.

Certain embodiments of the present disclosure provide a hydraulic system for an aircraft that includes a hydraulic monitoring control unit that is in communication with one or more sub-systems of the aircraft. The sub-systems, such as through electronic control units, output operational signals to the hydraulic monitoring control unit. In response to normal operational signals (for example, signals indicative of normal operation), the hydraulic monitoring control unit maintains hydraulic flow of hydraulic fluid to various components of the aircraft. In response to an altered operational signal from a sub-system, the hydraulic monitoring control unit operates one or more valves that are fluidly coupled to one or more components so that the hydraulic fluid is supplied to a first subset of the components, and bypassed from a second subset of components.

In at least one embodiment, the hydraulic monitoring control unit monitors the hydraulic power demands of the aircraft. In situations in which the hydraulic demands of a first subset of components (such as essential components) reach limits, the hydraulic monitoring control unit places actuators of the second subset of components (such as non-essential components) in a zero-demand state, in order to reserve hydraulic power for the first subset of components.

FIG. 1 illustrates a schematic block diagram of a hydraulic system 100 of an aircraft 102, according to an embodiment of the present disclosure. The hydraulic system 100 includes at least one fluid reservoir 104 that retains hydraulic fluid 106, such as an oil, water, and/or the like. One or more pumps 108 are configured to circulate the hydraulic fluid 106 through a fluid circuit 110 to components 112 (for example, actuators 114 operatively coupled to the components) of the aircraft 102. The components 112 are any components of the aircraft 102 that are hydraulically controlled. For example, the components 112 can include ailerons, spoilers, flaperons of wings, elevators of a horizontal stabilizer, a rudder of a vertical stabilizer, landing gear, and/or the like. The pumps 108 can include engine-driven pumps coupled to engines, electric motor pumps, air-driven pumps, and/or the like. The aircraft 102 can include more or less components 112 that are hydraulically-operated than shown.

Each component 112 is operated through one or more actuators 114, which are hydraulically-driven. The actuators 114 can be part of the components 112, or can be separate and distinct from the components 112. Each actuator 114 is in fluid communication with one or more valves 116 that are fluidly coupled to the fluid circuit 110. In at least one embodiment, each actuator 114 can include the respective valve(s) 116. Optionally, the actuators 114 can be separate and distinct from the valve(s) 116.

A hydraulic monitoring control unit 118 is in communication with the valves 116, such as through one or more wired or wireless connections. In at least one embodiment, the hydraulic monitoring control unit 118 is part of integrated flight control electronics. The hydraulic monitoring control unit 118 is configured to operate the valves 116 to control flow of the hydraulic fluid 106 to the components 112 (for example, to the actuators 114 that operate the components 112).

The hydraulic monitoring control unit 118 is also in communication with one or more sub-systems 120 of the aircraft 102, such as through one or more wired or wireless connections. Examples of the sub-systems 120 include engines, one or more of the pumps 108 (for example, while shown separately, one or of the pumps 108 can be a sub-system 120), a high pressure bleed sub-system, or the like.

The hydraulic monitoring control unit 118 is in communication with an electronic controller or control unit 122 of the sub-system 120. The control unit 122 monitors an operational status of the sub-system 120. For example, a control unit 122 of an engine, which is an example, of the sub-system 120, monitors an operational status of the engine. As another example, a control unit 122 of an engine-driven pump, which is an example of a pump 108 and can be a sub-system 120, monitors an operational status of the pump 108. The control unit 122 outputs an operational signal 124 to the hydraulic monitoring control unit 118.

When the sub-system 120 is operating in a normal state (for example, as intended to operate when active), the operational signal 124 is normal. The hydraulic monitoring control unit 118 analyzes the operational signal 124, determines that it is normal (for example, through pre-determined analysis via programming), and refrains from changing operation of the valves 116. That is, in response to the operational signal 124 being normal, the hydraulic monitoring control unit 118 ensures that that valves 116 operate normally to provide hydraulic fluid to all of the actuators 114.

If, however, the operational signal 124 is altered (indicating altered operation of the sub-system 120), the hydraulic monitoring control unit 118 operates a subset of the valves 116, such as valves 116 a, to bypass the hydraulic fluid 106 in relation to (that is, prevent, minimize, or otherwise reduce flow of the hydraulic fluid to) the associated actuators 114 a, so that the hydraulic fluid 106 is circulated to the remaining or subset of the valves 116, such as the valves 116 b. The valves 116 a can be associated with components 112 that are non-essential during a period of reduced hydraulic flow, due to the operational signal 124 being altered. The valves 116 b can be associated with components 112 that are essential during the period of reduced hydraulic flow. The hydraulic monitoring control unit 118 is programmed to provide the hydraulic fluid 106 to certain components, such as a first subset of component 112, which can be essential during periods of reduced flow of the hydraulic fluid 106 (as predetermined and programmed into the hydraulic monitoring control unit 118), and bypass fluid flow in relation to other components, such as a second subset of components 112, which can be non-essential during periods of reduced flow of the hydraulic fluid 106 (as predetermined and programmed into the hydraulic monitoring control unit 118).

An example of an altered operation of the sub-system 120 that results in the operational signal 124 being alerted is when the sub-system 120 is deactivated or operating at reduced capacity. For example, an engine can be deactivated when the aircraft 102 is on the ground during maintenance. As another example, an engine can be operating at a reduced capacity to conserve fuel. As another example, a high pressure bleed sub-system can be operating at a reduced capacity to conserve fuel. As another example, one of the pumps 108 can be deactivated when the aircraft 102 is on the ground during maintenance.

An operational status of an engine relates to flow of hydraulic fluid 106 within the hydraulic system 100. For example, total available hydraulic flow, measured in gallons per minute, when an engine is inactive is less than the flow of hydraulic fluid available when the engine is active. The engines include engine-driven pumps that operate to move the hydraulic fluid through the hydraulic system 100. When the engine is inactive, the engine-driven pumps are inactive. As such, remaining pumps (which are active even when the engine-driven pumps are active) that can not be as efficient as the engine-driven pumps are used to pump the hydraulic fluid. Consequently, when an engine is inactive, fluid flow rate within the hydraulic system is reduced. Accordingly, by monitoring the operational status of an engine, the fluid flow rate can also be monitored.

The hydraulic monitoring control unit 118 can operate the valves 116, such as by opening and closing the valves. In at least one embodiment, the valves 116 can be solenoid-operated valves, which the hydraulic monitoring control unit 118 operates through electronic control. For example, the hydraulic monitoring control unit 118 outputs valve control signals 126 that energize or de-energize the valves 116 to open or close fluid paths to and/or within the actuators 114.

In at least one embodiment, the valves 116 are initially set in a normal operating state that allows the hydraulic fluid to flow to the actuators 114. The hydraulic monitoring control unit 118 may not change such normal operating state of one or more of the valves 116 until the hydraulic monitoring control unit 118 receives an operational signal 124 from the sub-system 120 indicative of an altered operational state. In response, the hydraulic monitoring control unit 118 outputs the valve control signals 126 to the valves 116 a to bypass flow of the hydraulic fluid 106 with respect to the associated actuators 114 a. That is, in at least one embodiment, the valves 116 are configured to operate in a normal operating state, thereby supplying the hydraulic fluid 106 to all of the actuators 114 until the hydraulic monitoring control unit 118 receives the operational signal 124 indicative of an altered operational state of the sub-system 120, and, in response, outputs one or more valve control signals 126, which operate a subset of the valves 116 to bypass hydraulic fluid 106 with respect to (for example, around or otherwise away from) the associated actuators 114.

As described herein, embodiments of the present disclosure provide the hydraulic system 100 that includes the hydraulic monitoring control unit 118, which is configured to bypass hydraulic fluid 106 in relation to one or more actuators 114 in response to receiving an operational signal 124 indicating an altered operational state of the sub-system 120. The hydraulic fluid 106 is bypassed from actuators 114 of non-essential components 112, thereby ensuring that actuators 114 of the essential components 112 receive sufficient flow of hydraulic fluid 106. Accordingly, the hydraulic system 100 is configured to ensure sufficient hydraulic flow in relation to the components 112 of the aircraft 102 without the need for increasing a total amount of hydraulic fluid, additional pumps, or the like.

As described herein, the hydraulic system 100 includes the hydraulic monitoring control unit 118, which is configured to receive the operational signal 124 from the sub-system 120 of the aircraft 102, and control flow of the hydraulic fluid 106 to the actuators 114 of the components 112 based on the operational signal 124. The hydraulic monitoring control unit 118 bypasses the flow of the hydraulic fluid 106 in relation to a subset of the actuators 114 in response to the operational signal 124 indicating an altered operational state of the sub-system 120. The hydraulic monitoring control unit refrains from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.

As used herein, the term “control unit,” “central processing unit,” “unit,” “CPU,” “computer,” or the like can include any processor-based or microprocessor-based system including systems using microcontrollers, reduced instruction set computers (RISC), application specific integrated circuits (ASICs), logic circuits, and any other circuit or processor including hardware, software, or a combination thereof capable of executing the functions described herein. Such are exemplary only, and are thus not intended to limit in any way the definition and/or meaning of such terms. For example, the hydraulic monitoring control unit 118 can be or include one or more processors that are configured to control operation thereof, as described herein.

The hydraulic monitoring control unit 118 is configured to execute a set of instructions that are stored in one or more data storage units or elements (such as one or more memories), in order to process data. For example, the hydraulic monitoring control unit 118 can include or be coupled to one or more memories. The data storage units can also store data or other information as desired or needed. The data storage units can be in the form of an information source or a physical memory element within a processing machine.

The set of instructions can include various commands that instruct the hydraulic monitoring control unit 118 as a processing machine to perform specific operations such as the methods and processes of the various embodiments of the subject matter described herein. The set of instructions can be in the form of a software program. The software can be in various forms such as system software or application software. Further, the software can be in the form of a collection of separate programs, a program subset within a larger program or a portion of a program. The software can also include modular programming in the form of object-oriented programming. The processing of input data by the processing machine can be in response to user commands, or in response to results of previous processing, or in response to a request made by another processing machine.

The diagrams of embodiments herein can illustrate one or more control or processing units, such as the hydraulic monitoring control unit 118. It is to be understood that the processing or control units can represent circuits, circuitry, or portions thereof that can be implemented as hardware with associated instructions (e.g., software stored on a tangible and non-transitory computer readable storage medium, such as a computer hard drive, ROM, RAM, or the like) that perform the operations described herein. The hardware can include state machine circuitry hardwired to perform the functions described herein. Optionally, the hardware can include electronic circuits that include and/or are connected to one or more logic-based devices, such as microprocessors, processors, controllers, or the like. Optionally, the hydraulic monitoring control unit 118 can represent processing circuitry such as one or more of a field programmable gate array (FPGA), application specific integrated circuit (ASIC), microprocessor(s), and/or the like. The circuits in various embodiments can be configured to execute one or more algorithms to perform functions described herein. The one or more algorithms can include aspects of embodiments disclosed herein, whether or not expressly identified in a flowchart or a method.

As used herein, the terms “software” and “firmware” are interchangeable, and include any computer program stored in a data storage unit (for example, one or more memories) for execution by a computer, including RAM memory, ROM memory, EPROM memory, EEPROM memory, and non-volatile RAM (NVRAM) memory. The above data storage unit types are exemplary only, and are thus not limiting as to the types of memory usable for storage of a computer program.

While the hydraulic systems and methods described herein are described with respect to an aircraft, the hydraulic systems and methods can be optionally used with various other vehicles (such as automobiles, locomotives, watercraft, spacecraft, and the like).

FIG. 2 illustrates a front perspective view of the aircraft 102, according to an exemplary embodiment of the present disclosure. The aircraft 102 includes a propulsion system 212 that can include two engines 214, for example. In at least one embodiment, each of the engines 214 is an example of a sub-system 120 (shown in FIG. 1). Optionally, the propulsion system 212 can include more engines 214 than shown. The engines 214 are carried by wings 216 of the aircraft 102. In other embodiments, the engines 214 can be carried by a fuselage 218 and/or an empennage 220. The empennage 220 can also support horizontal stabilizers 222 and a vertical stabilizer 224. The fuselage 218 of the aircraft 102 defines an internal cabin, which can include a cockpit 230, one or more work sections (for example, galleys, personnel carry-on baggage areas, and the like), and/or one or more passenger sections. The hydraulic monitoring control unit 118 (shown in FIG. 1) can be located within the cockpit 230 (such as part of integrated flight control electronics), within an internal cabin, such as part of a computer workstation, or the like. The aircraft 102 includes the hydraulic system 100 and the various components 112 (shown in FIG. 1).

FIG. 3 illustrates a schematic diagram of components 112 of the aircraft, according to an embodiment of the present disclosure. The components 112 include ailerons 300, spoilers 302, and flaperons 304 of the wings 216, elevators 306 of the horizontal stabilizer 222, and a rudder 112 of the vertical stabilizer 224.

Referring to FIGS. 1-3, the sub-system 120 can be an engine 214 of the aircraft 102. In response to the engine 214 operating in an altered state, the control unit 122 of the engine 214 outputs the operational signal 124 indicating altered operation of the engine 214. The hydraulic monitoring control unit 118 receives the operational signal 124 indicating the altered operation, and controls valves in fluid communication with actuators 114 a to bypass flow of the hydraulic fluid 106 in relation to (for example, around or otherwise away from) the actuators 114 a. The hydraulic monitoring control unit 118 is preprogrammed to identify the particular actuators 114 a in response to the operational signal 124 indicating altered operation of the engine 214. As shown, the hydraulic monitoring control unit 118 can bypass fluid flow in relation to one actuator 114 on each multi-actuator surface (for example, each component 112), such as when the bypassed actuator 114 is not needed.

The location and number of the actuators 114 can differ than shown in FIG. 3. It is to be understood that FIG. 3 is merely an example to show that flow of the hydraulic fluid 106 is bypassed in relation to a subset of the actuators 114 a.

FIG. 4 illustrates a schematic diagram of an actuator 114 operating in a normal state, according to an embodiment of the present disclosure. The actuator 114 can include various valves, or the valves can be separate from the actuator 114. The actuator 114 includes a fluid inlet 400 that connects to a fluid inlet path 402. A first valve 404 is disposed within the fluid inlet path 402. In at least one embodiment, the first valve 404 is an actuator position control valve or actuator rate control valve. A second valve 406 is disposed within the fluid inlet path 402 downstream from the first valve 404. In at least one embodiment, the second valve 406 is a mode select valve. The fluid inlet path 402 connects to a piston 410. The piston 410 is also in fluid communication with a fluid outlet path 412. The second valve 406 is also within a fluid outlet path 412. The first valve 404 is in the fluid outlet path 412 downstream from the second valve 406. A fluid outlet 414 of the fluid outlet path 412 is downstream from the first valve 404.

During normal operation, hydraulic fluid 106 (shown in FIG. 1) passes into the fluid inlet 400 from the fluid circuit 110 (shown in FIG. 1). The first valve 404 is in the null position (unless flight control surface(s) connected to the actuator is to be positioned, at which point the first valve 404 is connected to the off-null position), and the second valve 406 is in the active mode position, thereby allowing the hydraulic fluid 106 to flow through the fluid inlet path 402 to the piston 410, and through the fluid outlet path 412, out of the fluid outlet 414, and back to the fluid circuit 110.

FIG. 5 illustrates a schematic diagram of the actuator having a bypass valve 416 (such as a solenoid operated valve) in a bypass position, according to an embodiment of the present disclosure. Referring to FIGS. 1 and 5, the bypass valve 416, the first valve 404, and the second valve 406 are examples of the valves 116.

In at least one embodiment, the second valve 406 is not electronically controlled. Rather, the second valve 406 is indirectly controlled by the same signal that controls the bypass valve 416 through a hydraulic pilot pressure path within the actuator linking the hydraulic supply and the second valve 406. The bypass valve 416 and the second valve 406 can be part of a single valve, for example.

In response to receiving the operational signal 124 indicating altered operation of the sub-system 120, the hydraulic monitoring control unit 118 outputs a valve control signal 126 which de-energizes (or alternatively, energizes) the bypass valve 416 to move in the direction of arrow A into a bypass position, which causes the second valve 406 to move in the direction of arrow B, thereby preventing fluid flow within the fluid inlet path 402 to the piston 410, and connecting together the fluid paths of the actuator extend and retract sides of piston 410. In this manner, the actuator 114 is isolated from the fluid circuit 110. Similarly, an actuator position command signal, such as the valve control signal 126, energizes (or alternatively, de-energizes) the first valve 404 so that the first valve 404 is moved in the direction of arrow C to an off-null position. As such, a bypass fluid flow path, such as an actuator fluid flow path 420 with lower than nominal internal leakage, is formed. The actuator fluid flow path 420 is formed primarily through the first valve 404 being commanded to a position that yields lower internal leakage through the valve in response to the valve control signal 126. With the piston 410 isolated, the capacity of the fluid circuit 110 is relieved of demand from the actuator 114, and the first valve 404 is also able to be commanded to a position that yields lower actuator internal leakage.

As noted, each of the bypass valve 416, the first valve 404, and the second valve 406 are examples of the valves 116 shown in FIG. 1. It is to be understood that the schematics shown in FIGS. 4 and 5 are merely exemplary. The actuator 114 can include, or otherwise be in fluid communication with, more or less valves than shown. For example, a single valve (such as the bypass valve 416) can be operated to form a bypass fluid flow path that bypasses fluid from the actuator 114 so that the fluid does not flow to an operable portion of the actuator 114, such as the piston 410.

FIG. 6 illustrates a flow chart of a hydraulic control method for an aircraft, according to an embodiment of the present disclosure. Referring to FIGS. 1 and 6, at 500, the hydraulic monitoring control unit 118 receives the operational signal 124 from the sub-system 120. At 502, the hydraulic monitoring control unit 118 determines if the operational signal 124 is indicative of normal operation of the sub-system 120. If the operational signal 124 is indicative of the normal operation, the method proceeds to 504, at which the hydraulic monitoring control unit 118 refrains from altering operation of the valves 116, thereby allowing the hydraulic fluid to flow to the actuators 114 associated with the components 112.

If, however, the operational signal 124 is not indicative of normal operation, but is instead indicative of altered operation, the method proceeds from 502 to 506, at which the hydraulic monitoring control unit 118 operates (such as through the valve control signal(s) 126) one or more of the valves 116 a (for example, a subset of the valves 116) to bypass the hydraulic fluid 106 in relation to one or more of the actuators 114 a (for example, a subset of the actuators 114) associated with the valves 116 a.

At 508, the hydraulic monitoring control unit 118 continues to monitor the operational signal 124 to determine if the sub-system 120 is operating in a normal state (for example, as intended to operate when active). If not, the method returns to 506. If, however, the sub-system 120 is not operating normally, the method proceeds from 508 to 510, at which the hydraulic monitoring control unit 118 operates the valve(s) 116 to move back to normal operating positions (and therefore the hydraulic fluid is no longer bypassed in relation to the subset of actuators 114). The method then returns to 500.

As described herein, embodiments of the present disclosure provide efficient systems and methods of managing hydraulic demand of an aircraft. Further, embodiments of the present disclosure provide systems and methods of managing hydraulic demand of an aircraft without adding weight to the aircraft.

Further, the disclosure comprises embodiments according to the following clauses:

Clause 1: A hydraulic system, the hydraulic system comprising:

a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of a vehicle and control flow of hydraulic fluid to actuators of components of the vehicle based on the operational signal, and wherein the hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

Clause 2. The hydraulic system of Clause 1, wherein the hydraulic monitoring control unit is configured to refrain from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.

Clause 3. The hydraulic system of Clauses 1 or 2, further comprising one or more pumps fluidly coupled to the actuators through a fluid circuit, wherein the one or more pumps are configured to circulate the hydraulic fluid with respect to the actuators.

Clause 4. The hydraulic system of Clauses 1, 2, or 3, wherein the components comprise:

at least one of ailerons, spoilers, flaperons or wings of an aircraft;

elevators of a horizontal stabilizer of the aircraft; and

a rudder of a vertical stabilizer of the aircraft.

Clause 5. The hydraulic system of Clauses 1-3 or 4, further comprising one or more valves in fluid communication with the actuators, wherein the hydraulic monitoring control unit is configured to control the one or more valves to control the flow of hydraulic fluid to the actuators of the components.

Clause 6. The hydraulic system of Clauses 1-4 or 5, wherein the sub-system comprises at least one engine.

Clause 7. The hydraulic system of Clauses 1-5 or 6, wherein the sub-system comprises at least one pump.

Clause 8. The hydraulic system of Clauses 1-6 or 7, wherein at least one of the actuators comprises:

a fluid inlet connected to a fluid inlet path;

a first valve disposed within the fluid inlet path;

a second valve disposed within the fluid inlet path downstream from the first valve;

a piston connected to the fluid inlet path;

a fluid outlet path connected to the piston and having a fluid outlet, wherein the first valve and the second valve are also disposed within the fluid outlet path;

and

a bypass valve.

Clause 9. The hydraulic system of Clauses 1-7 or 8, wherein the hydraulic monitoring control unit is configured to control the first valve, the second valve, and the bypass valve to form a bypass fluid flow path that prevents the hydraulic fluid from passing to the piston in response to the operational signal indicating the altered operational state of the sub-system.

Clause 10. A method comprising:

receiving, by a hydraulic monitoring control unit, an operational signal from a sub-system of a vehicle; and

controlling, by the hydraulic monitoring control unit, flow of hydraulic fluid to actuators of components based on the operational signal, wherein said controlling comprises bypassing the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

Clause 11. The hydraulic control method of Clause 10, wherein said controlling comprises refraining from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.

Clause 12. The hydraulic control method of Clauses 10 or 11, further comprising:

fluidly coupling one or more pumps fluidly to the actuators through a fluid circuit; and

circulating, by the one or more pumps, the hydraulic fluid with respect to the actuators.

Clause 13. The hydraulic control method of Clauses 10, 11, or 12, wherein the components comprise:

at least one of ailerons, spoilers, flaperons or wings of an aircraft;

elevators of a horizontal stabilizer of the aircraft; and

a rudder of a vertical stabilizer of the aircraft.

Clause 14. The hydraulic control method of Clauses 10-12 or 13, wherein said controlling further comprises controlling one or more valves to control the flow of hydraulic fluid to the actuators of the components.

Clause 15. The hydraulic control method of Clauses 10-13 or 14, wherein the sub-system comprises at least one engine.

Clause 16. The hydraulic control method of Clauses 10-14 or 15, wherein the sub-system comprises at least one pump.

Clause 17. The hydraulic control method of Clauses 10-15 or 16, wherein said controlling comprises controlling a first valve, a second valve, and a bypass valve of at least one of the actuators to form a bypass fluid flow path that prevents the hydraulic fluid from passing to a piston of the at least one of the actuators in response to the operational signal indicating the altered operational state of the sub-system.

Clause 18. An aircraft comprising:

a sub-system;

components;

actuators operatively coupled to the components; and

a hydraulic system comprising:

one or more pumps fluidly coupled to the actuators through a fluid circuit, wherein the one or more pumps are configured to circulate the hydraulic fluid with respect to the actuators; and

a hydraulic monitoring control unit configured to receive an operational signal from the sub-system of the aircraft and control flow of hydraulic fluid to the actuators based on the operational signal,

wherein the hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system, and

wherein the hydraulic monitoring control unit is configured to refrain from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.

Clause 19. The aircraft of Clause 18, wherein the sub-system comprises at least one engine, and wherein the components comprise:

at least one of ailerons, spoilers, flaperons or wings of the aircraft;

elevators of a horizontal stabilizer of the aircraft; and

a rudder of a vertical stabilizer of the aircraft.

Clause 20. The aircraft of Clauses 18 or 19, wherein at least one of the actuators comprises:

a fluid inlet connected to a fluid inlet path;

a first valve disposed within the fluid inlet path;

a second valve disposed within the fluid inlet path downstream from the first valve;

a piston connected to the fluid inlet path;

a fluid outlet path connected to the piston and having a fluid outlet, wherein the first valve and the second valve are also disposed within the fluid outlet path;

and

a bypass valve,

wherein the hydraulic monitoring control unit is configured to control the first valve, the second valve, and the bypass valve to form a bypass fluid flow path that prevents the hydraulic fluid from passing to the piston in response to the operational signal indicating the altered operational state of the sub-system.

While various spatial and directional terms, such as top, bottom, lower, mid, lateral, horizontal, vertical, front and the like can be used to describe embodiments of the present disclosure, it is understood that such terms are merely used with respect to the orientations shown in the drawings. The orientations can be inverted, rotated, or otherwise changed, such that an upper portion is a lower portion, and vice versa, horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configured to” perform a task or operation is particularly structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and the avoidance of doubt, an object that is merely capable of being modified to perform the task or operation is not “configured to” perform the task or operation as used herein.

It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described embodiments (and/or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of the various embodiments of the disclosure without departing from their scope. While the dimensions and types of materials described herein are intended to define the parameters of the various embodiments of the disclosure, the embodiments are by no means limiting and are exemplary embodiments. Many other embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the various embodiments of the disclosure should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims, the terms “including” and “in which” are used as the plain-English equivalents of the respective terms “comprising” and “wherein.” Moreover, the terms “first,” “second,” and “third,” etc. are used merely as labels, and are not intended to impose numerical requirements on their objects. Further, the limitations of the following claims are not written in means-plus-function format and are not intended to be interpreted based on 35 U.S.C. § 112(f), unless and until such claim limitations expressly use the phrase “means for” followed by a statement of function void of further structure.

This written description uses examples to disclose the various embodiments of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the various embodiments of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various embodiments of the disclosure is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements with insubstantial differences from the literal language of the claims. 

What is claimed is:
 1. A hydraulic system, the hydraulic system comprising: a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of a vehicle and control flow of hydraulic fluid to actuators of components of the vehicle based on the operational signal, and wherein the hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.
 2. The hydraulic system of claim 1, wherein the hydraulic monitoring control unit is configured to refrain from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.
 3. The hydraulic system of claim 1, further comprising one or more pumps fluidly coupled to the actuators through a fluid circuit, wherein the one or more pumps are configured to circulate the hydraulic fluid with respect to the actuators.
 4. The hydraulic system of claim 1, wherein the components comprise: at least one of ailerons, spoilers, flaperons or wings of an aircraft; elevators of a horizontal stabilizer of the aircraft; and a rudder of a vertical stabilizer of the aircraft.
 5. The hydraulic system of claim 1, further comprising one or more valves in fluid communication with the actuators, wherein the hydraulic monitoring control unit is configured to control the one or more valves to control the flow of hydraulic fluid to the actuators of the components.
 6. The hydraulic system of claim 1, wherein the sub-system comprises at least one engine.
 7. The hydraulic system of claim 1, wherein the sub-system comprises at least one pump.
 8. The hydraulic system of claim 1, wherein at least one of the actuators comprises: a fluid inlet connected to a fluid inlet path; a first valve disposed within the fluid inlet path; a second valve disposed within the fluid inlet path downstream from the first valve; a piston connected to the fluid inlet path; a fluid outlet path connected to the piston and having a fluid outlet, wherein the first valve and the second valve are also disposed within the fluid outlet path; and a bypass valve.
 9. The hydraulic system of claim 8, wherein the hydraulic monitoring control unit is configured to control the first valve, the second valve, and the bypass valve to form a bypass fluid flow path that prevents the hydraulic fluid from passing to the piston in response to the operational signal indicating the altered operational state of the sub-system.
 10. A method comprising: receiving, by a hydraulic monitoring control unit, an operational signal from a sub-system of a vehicle; and controlling, by the hydraulic monitoring control unit, flow of hydraulic fluid to actuators of components based on the operational signal, wherein said controlling comprises bypassing the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.
 11. The method of claim 10, wherein said controlling comprises refraining from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.
 12. The method of claim 10, further comprising: fluidly coupling one or more pumps fluidly to the actuators through a fluid circuit; and circulating, by the one or more pumps, the hydraulic fluid with respect to the actuators.
 13. The method of claim 10, wherein the components comprise: at least one of ailerons, spoilers, flaperons or wings of an aircraft; elevators of a horizontal stabilizer of the aircraft; and a rudder of a vertical stabilizer of the aircraft.
 14. The method of claim 10, wherein said controlling further comprises controlling one or more valves to control the flow of hydraulic fluid to the actuators of the components.
 15. The method of claim 10, wherein the sub-system comprises at least one engine.
 16. The method of claim 10, wherein the sub-system comprises at least one pump.
 17. The method of claim 10, wherein said controlling comprises controlling a first valve, a second valve, and a bypass valve of at least one of the actuators to form a bypass fluid flow path that prevents the hydraulic fluid from passing to a piston of the at least one of the actuators in response to the operational signal indicating the altered operational state of the sub-system.
 18. An aircraft comprising: a sub-system; components; actuators operatively coupled to the components; and a hydraulic system comprising: one or more pumps fluidly coupled to the actuators through a fluid circuit, wherein the one or more pumps are configured to circulate the hydraulic fluid with respect to the actuators; and a hydraulic monitoring control unit configured to receive an operational signal from the sub-system of the aircraft and control flow of hydraulic fluid to the actuators based on the operational signal, wherein the hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system, and wherein the hydraulic monitoring control unit is configured to refrain from bypassing the flow of the hydraulic flow in relation to the subset of the actuators in response to the operational signal indicating a normal operational state of the sub-system.
 19. The aircraft of claim 18, wherein the sub-system comprises at least one engine, and wherein the components comprise: at least one of ailerons, spoilers, flaperons or wings of the aircraft; elevators of a horizontal stabilizer of the aircraft; and a rudder of a vertical stabilizer of the aircraft.
 20. The aircraft of claim 18, wherein at least one of the actuators comprises: a fluid inlet connected to a fluid inlet path; a first valve disposed within the fluid inlet path; a second valve disposed within the fluid inlet path downstream from the first valve; a piston connected to the fluid inlet path; a fluid outlet path connected to the piston and having a fluid outlet, wherein the first valve and the second valve are also disposed within the fluid outlet path; and a bypass valve, wherein the hydraulic monitoring control unit is configured to control the first valve, the second valve, and the bypass valve to form a bypass fluid flow path that prevents the hydraulic fluid from passing to the piston in response to the operational signal indicating the altered operational state of the sub-system. 